CN102837433B - Laying-up method for non-planar composite material components - Google Patents

Laying-up method for non-planar composite material components Download PDF

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Publication number
CN102837433B
CN102837433B CN201210169245.8A CN201210169245A CN102837433B CN 102837433 B CN102837433 B CN 102837433B CN 201210169245 A CN201210169245 A CN 201210169245A CN 102837433 B CN102837433 B CN 102837433B
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Prior art keywords
track
predetermined value
laying
band
composite material
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CN201210169245.8A
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CN102837433A (en
Inventor
阿尔韦托·洛扎诺塞维利亚
约瑟·奥伦西奥·格拉纳多马卡里利亚
文森特·马丁内斯巴尔德格拉马
劳尔·布尔戈斯加列戈
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Airbus Operations SL
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Airbus Operations SL
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/386—Automated tape laying [ATL]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24628—Nonplanar uniform thickness material
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24628—Nonplanar uniform thickness material
    • Y10T428/24669—Aligned or parallel nonplanarities

Abstract

The invention relates to a laying-up method for non-planar composite material components and in particular relates to a method for laying-up the tapes of a prepeg composite material in the 0 DEG direction of a non-planar composite component on a suitable mould using an ATL machine comprising steps of: a) determining the trajectories of said tapes as modified trajectories of geodesic trajectories complying with the following conditions in their projections in an horizontal plane: that the radius of curvature R 2 of their curved segments is bigger than a predetermined value R min ; that the gap G2p between two contiguous tapes is comprised between 0 and a predetermined value G max ; b) providing said modified trajectories to said ATL machine. A non-planar composite component such as an skin of an aircraft wing having the tapes in the 0 DEG direction following trajectories complying with said conditions is also disclosed.

Description

The lay-up method of on-plane surface composite material component
Technical field
The present invention relates to the manufacture of composite material component, and in specific words, relate to and use automation belt spreading machine to manufacture on-plane surface composite material component, the torsion box shell of the such as aircraft wing.
Background technology
Composite material component manufacture method comprises laying stage and cure stage, and in the laying stage, the composite layer of rolling is arranged on the mould of suitable shape, and cure stage is then know in aircraft industry and other industry.
The composite the most often used in aircraft industry is made up of the fiber be embedded in thermosetting or thermoplastic resin matrix or fibre bundle, and its form is pre-preg or " pre-preg " material.Their main advantage refers to:
-they are relative to the high specific strength of metal material;
-their splendid performances under fatigue loads;
-structure optimization the possibility that caused by material anisotropy and conjugate fiber and the possibility of different orientation, make it possible to according to executed loaded different demand and regulate the element designs with different mechanical attributes.
Composite layer is not random setting, but strengthens orientation arrangement in each district with a certain number and its fiber (being generally carbon fiber), and this stress characteristics of bearing according to parts in each district and size are determined.Thus, each district has stacking according to floor or arranges and fixed ad hoc structure.Thickness difference not between same district can reduce by trigger layer, and this needs to make each parts have layer model, and how described layer model arranges layer during stacking process on fixture if establishing.
The automation belt spreading machine (hereinafter referred to ATL machine) that usual use is used for unidirectional laying (UD) or fabric strip performs the laying stage.Band is laid immediately on mould according to component shape, and its reinforcing fibre is in the orientation that designer determines.Then ATL machine should possess the track that laying composite material tape (being generally CFRP pre-preg) should be followed.
Along the band track in 0 ° of direction in contoured surface, should following " natural route " in the ideal case, that is can not stretch following contoured surface or folding path with when laying.
But the determination of described " natural route " of non-planar surfaces is very difficult.
In the first scheme, propose determine along the band track in 0 ° of direction be geodesic curve (namely, the curve straight relative to local, surface, because its geodesic curvature equals zero at each point), but find, these tracks relate to crosses wide arc gap between the adjacent typical sizes band that uses in the industry.
US 2006/0073309 discloses a kind of method in order to calculate as the band track along 0 ° of direction of the track determined by a plurality of natural route segmentation, which obviate described wide arc gap excessively, also avoid and form fold on tape, each band track both defines the non-natural angle relative to path adjacent sectional, to make in the horizontal edge of each band is arranged on and adjacent belts is predetermined offset distance interval.Large composite portion (such as having the aircraft wing shell of hyperbolicity) for complex geometric shapes implements the method, relates to computational problem, and cannot guarantee not produce fold.
Thus need a kind of lay-up method, wherein should easily calculate described ideal trajectory and provide described ideal trajectory to ATL machine.
Summary of the invention
A target of the present invention is the method using ATL machine pre-preg composite material tape along 0 ° of direction of laying on-plane surface composite component on suitable mould, and wherein said band track is defined as making them can not produce fold by ATL machine laying.
A target of the present invention is the method using ATL machine pre-preg composite material tape along 0 ° of direction of laying on-plane surface composite component on suitable mould, wherein can calculate described band track easily.
An also target of the present invention is to provide on-plane surface composite component, and it has the composite material tape suitably laid, to avoid various defect, and the excess play such as between fold, continuous band and the overlap between continuous band.
In one aspect, these and other targets are realized by the method for a kind of ATL of use machine pre-preg composite material tape along 0 ° of direction of laying on-plane surface composite component on suitable mould, the method comprises the steps: a) to determine the amendment track of described band track as geodetic track, meets following condition: the radius of curvature R of its curved section in its projection in the horizontal plane 2be greater than predetermined value R min; Clearance G between two adjacent belts 2pbe included in 0 and predetermined value G maxbetween; B) described amendment track is provided to described ATL machine.
In an embodiment of the present invention, described step a) comprises following sub-step: a1) project in the horizontal plane and be with corresponding geodetic track with described; A2) floor projection track is revised to meet above-mentioned condition; A3) by described surface and intersecting containing the vertical plane of horizontal trajectory revised to some extent, the track of described amendment is obtained on the surface at the laying of correspondence.Therefore, for providing a kind of method using hardware and software to implement, described hardware and software uses ATL machine to obtain in lay-up process usually.
In an embodiment of the present invention ,-described predetermined value R minthe band being 300mm for width is 400mm; And described predetermined value G maxfor 3.5mm.Therefore, provide a kind of so method, the track wherein along 0 ° of direction conforms to quality requirements.
In an embodiment of the present invention, described parts are aircraft wing shells.Therefore, a kind of method along 0 ° of direction laying band in large complex geometric shapes parts allowing the process of automation laying is provided.
In one aspect of the method, above-mentioned target is realized by a kind of on-plane surface composite component (especially aircraft wing shell), and this on-plane surface composite component comprises to be followed its projection in a horizontal plane and meet the track of following condition and the composite material tape along 0 ° of direction that arranges: the radius of curvature R of its curved section 2be greater than predetermined value R min; Clearance G between two adjacent belts 2pbe included between 0 and predetermined value Gmax.
At reference accompanying drawing to illustrating in the detailed description of embodiment of target of the present invention, more easily other characteristics of the present invention and advantage will be understood.
Accompanying drawing explanation
Fig. 1 shows the schematic plan view of aircraft wing shell.
Fig. 2 shows the typical cross-section in a described shell district.
Fig. 3 a diagrammatically illustrates the projection on the horizontal plane in a described shell district, and wherein three adjacent belts are arranged according to known geodetic track.
Fig. 3 b diagrammatically illustrates the cross section of Fig. 3 a along plane A-A and B-B.
Fig. 4 a diagrammatically illustrates the projection on the horizontal plane in a described shell district, and wherein three adjacent belts are arranged according to the track determined according to the present invention.
Fig. 4 b diagrammatically illustrates the cross section of Fig. 4 a along plane A-A and B-B.
Detailed description of the invention
The automated procedures in the laying stage in composite material component manufacture method are known in the art.ATL facility have the movable belt delivery head mechanism be arranged between closed slide, and it can move along multiple axle thus pre-preg band is placed in multiple grinding tool in shape.Pre-preg band (be generally rolling arrange) containing the uncured composite be retained on backing paper, this backing paper removable when band is placed on mould.
When laying particular elements, the track determined along considering morphology and the suitable packing of orders, the band delivery head mechanism of motion ATL machine and lay band.Predetermined form can provide these tracks to ATL machine, and available process component can be used in ATL machine to form these tracks.
The band track along 0 ° of direction of the shell 11 determining the aircraft wing torsion box represented in FIG according to the present invention will be described now.Fig. 2 shows the cross section in the district 15 of described shell 11, there is notable difference between the length of the curve 17 of the shell 11 in described cross section and described curve 17 projector distance D in the horizontal plane.The D/L in each district of shell 11 is than changing.
Starting point is the track (normally based on the track of geodetic) that the calculating component of the ATL machine of current use provides.
Fig. 3 a shows the start track of three bands 21,23,25 that the described district 15 on the shell laying surface be projected on ground level (horizontal plane) lays.Fig. 3 b shows described district 15 along plane A-A (having high D/L ratio) and the cross section along plane B-B (having lower D/L ratio).
(Fig. 3 is a) there is constant clearance G between band 21,23,25 to projection start track on ground level 1pparallel track, and in those districts of shell with lower D/L ratio, there is certain curvature radius (R1).On laying surface (Fig. 3 b), the band 21,23,25 in cross section, A-A and the clearance G between the band 21,23,25 in cross section B-B 1s, can change under preset limit.If these limit cause described radius R 1little, be so with 21,23,25 to be laid on laying on the surface with a tension force, this can cause having described radius of curvature R 1region in produce fold.R 1lower, tension force is higher, and more early occurs fold.Therefore, R 1should have insurmountable minimum of a value, this occurs in many cases, but can not occur under the large parts of complex curvatures of such as large wing shell,
Fig. 4 a shows the track of three bands 21,23,25 in the described district 15 being laid on shell laying surface that to be projected to according to the present invention on ground level, and Fig. 4 b shows described district 15 along plane A-A (have large D/L than) and the cross section along plane B-B (have lower D/L than).
(Fig. 4 is a) have variable gap G between band 21,23,25 to the projected footprint up at ground level 2pnot parallel track, and on those shell region with lower D/L ratio, there is radius of curvature R 2>R 1, like this, band 21,23,25 be laid on have compared with low-tension laying on the surface, and avoid fold produce.
On laying surface (Fig. 4 b), the clearance G between the band 21,23,25 in cross section, A-A 2ssimilar with situation before, but at cross section B-B intermediate gap G 2slarger.Therefore can accept, the clearance G between band 2sthan larger in those regions with lower D/L ratio, predetermined value G can be exceeded in no instance max.
Determine that the operation procedure of track comprises the following steps:
A) revise the start track projection on ground level, like this, their curved section has than predetermined least radius R minlarger radius of curvature R 2, and gap is included in 0 and maximum predetermined value G maxbetween;
B) by described surface and the intersecting of vertical plane containing described amendment track, track is obtained on the surface at the laying of correspondence.
According to the experimental data that inventor obtains, can good result be obtained by the following value of above-mentioned parameter:
R min=400mm (bandwidth for 300mm);
G max＝3.5mm。
Notice, if along in the band track in 0 ° of direction, the length difference between two borders of the band in given zone, more than 2.5mm, so there will be fold.In track according to the present invention, described length difference can not more than 2.5mm.
Although describe the present invention completely in conjunction with the preferred embodiments, clearly, can introduce numerous amendment within the scope of the invention, scope of the present invention can't help the restriction of these embodiments, but is limited by the content of following claim.

Claims (5)

1. use a method for ATL machine pre-preg composite material tape along 0 ° of direction of laying on-plane surface composite component on suitable mould, it is characterized in that, comprise the following steps:
A) determine the amendment track of described band track as geodetic track, in the projection in the horizontal plane of band track, meet following condition:
The radius of curvature R of-its curved section 2be greater than predetermined value R min;
Clearance G between-two adjacent belts 2pbe included in 0 and predetermined value G maxbetween;
-described predetermined value R minthe band being 300mm for width is 400mm;
-described predetermined value G maxfor 3.5mm;
B) described amendment track is provided to described ATL machine.
2. method according to claim 1, is characterized in that, wherein said step a) comprises following sub-step:
A1) projection is with corresponding geodetic track with described in the horizontal plane;
A2) described floor projection track is revised to meet above-mentioned condition;
A3) by described surface and intersecting containing the vertical plane of horizontal trajectory revised to some extent, the track of described amendment is obtained on the surface at the laying of correspondence.
3. method according to claim 1 and 2, is characterized in that, described parts are aircraft wing shells.
4. an on-plane surface composite component, comprises and follows composite material tape projection in a horizontal plane and meet the track of following condition and the composite material tape along 0 ° of direction arranged:
The radius of curvature R 2 of-its curved section is greater than predetermined value R min;
Clearance G 2p between-two adjacent belts is included in 0 and predetermined value G maxbetween;
-described predetermined value R minthe band being 300mm for width is 400mm;
-described predetermined value G maxfor 3.5mm.
5. on-plane surface composite component according to claim 4, is characterized in that, described parts are aircraft wing shells.
CN201210169245.8A 2011-05-27 2012-05-26 Laying-up method for non-planar composite material components Active CN102837433B (en)

Applications Claiming Priority (2)

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ES201130883A ES2400131B1 (en) 2011-05-27 2011-05-27 STACKING METHOD FOR COMPONENTS OF NON-FLAT COMPOSITE MATERIAL
ES201130883 2011-05-27

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ES2400131B1 (en) 2014-04-29
RU2012121691A (en) 2013-11-27
ES2693118T3 (en) 2018-12-07
ES2400131R1 (en) 2013-06-17
EP2527130A1 (en) 2012-11-28
EP2527130B1 (en) 2018-08-22
RU2603791C2 (en) 2016-11-27
US8649897B2 (en) 2014-02-11
US20120301681A1 (en) 2012-11-29
CA2778014C (en) 2020-04-21
CA2778014A1 (en) 2012-11-27
CN102837433A (en) 2012-12-26
ES2400131A2 (en) 2013-04-05

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